Gas turbine installation



April M. H. L. SEDILLE GAS TURBINE INSTALLATION Filed March '16, 1942 Variable d beed 771a tor- Fig-3 I f Gene ra tor C Tm Ta Genera for i V [Tn/enfor- MARCEL h. L. JED/L15 Patented Apr. 24, 1945 GAS TURBINE INSTALLATION Marcel Henri Louis S-dille, Paris, France; vested in the Alien Property Custodian Application March 16, 1942, Serial No. 434,986 In France March 29, 1941 1 Claim. (Cl. 6041) In gas turbine installations operating on liquid or solid fuels, the fuel control'is obtained with power losses which represent only a small fraction of the total power. In installations which utilize gaseous fuels (blast furnace gases, coke furnace gases, producer gas, etc.) the gas compressor consumes an appreciable power which is a relatively important fraction of the total compression power. It is important therefore, in order that the over-all efiiciency of the system remains good, that the regulations of the fuel supply be effected with the smallest power losses. It is also desirable that the operating point of the gas compressor on its characteristic curve vary only a little, so that its yield will be maintained in the proximity of the maximum value.

The present invention attains this double object,

According to an embodiment of the invention, the calorific power of the combustible gas is controlled at the suction end of the compressor of this gas, either by diminishing it, or by increasing it, or by both of these means concurrently, according to the load of the installations.

The increase of the calorific power of the combustible gas may be obtained by mixing it with a richer gaseous fuel (coke furnace gas, acetylene, natural gas, gas produced by the distillation of coal, etc.) or by vaporization of a suitable liquid fuel (butane). The reduction may be obtained by mixing it with a poorer combustible gas (blast furnace gas, poor gas) or by mixing it with air or with inert gases (cooled combustion gases).

The description which will follow with reference to the appended drawin given byway of non limitative example will allow a thorough understanding of how the invention can be embodied, those peculiarities which appear in the text as well as in the drawing constituting of course, a part of the invention.

Figures 1, 2, 3, 4, 5, 6 are diagrammatical views relating to the various embodiments of the invention.

Figure 1 represents, only by way of example, a gas turbine installation of the simplest type, that is to say comprising an air compressor C and a combustible gas compressor G operated by the same auxiliary turbine Ta. The motive turbine Tm is supposed to be connected in parallel with the auxiliary turbine Ta. The conduit 0 for the main gaseous fuel is connected to the suction end of the -compressor G in parallel with a conduit 0' for the richer gaseous fuel. The regulation of the richness of the fuel admitted into the comchamber Ch is obtained by simultaneously operating the two valves 0 and'O', it being possible to calculate or determine by experimentation the simultaneous position of these two organs, so as to allow a total gas supply of such a value that the operating point of the compressor G on its characteristic curve be maintained in the proximity of the maximum yield point.

The conduit 0 can also be a suction conduit for sucking in air or an inert gas, or it can be a conduit for a gas poorer than the one mainly used. Regulation by the richer gas or by the poorer gas can be indifierently resorted to, the compressors C and G not having the same sizes or dimensions in both cases, as can be easily understood. I

Figure 2 is a modified form in which two fans V and V are utilized instead of the two valves 0 and O. The regulation is obtained by acting on the speed of the motors M and M which drive these fans and these two simultaneous actions can also be carried on in such a way as to keep the compressor G's operating point substantially constant.

Naturally, in both these cases, the regulation could be elfected With only one valve or on only one of the fans. There can even be only one valve or only one fan, if'the pressure in one of the conduits is greater or lower than in the other.

Of course, these arrangements can be utilized in conjunction with any arrangements whatever adopted for the installation of the gas turbine motive unit itself. In particular, the gas compressor G may be mounted on a shaft distinct from that of the air compressor C.

Figure 3 relates to the second way of embodying the invention. Thegas compressor G is operated by a special motive unitin the present example, a small gas turbine T'which may be connected to the others in series or in parallel. In the example shown, this turbine T is connected in parallel with the turbines Ta and Tm. The regulating of the quantity of combustible gas fed to the combustion chamber Ch. is then effected on the governing motive unit T, for example, by more or less closing, by means of the valve 0', the inlet of hot gases actuating this turbine.

Figure 4 is a modified form of the preceding embodiment in which the compressor Gof the gaseous fuel is operated by an electric motor M on which the control means act. This motor receives its power from a shunt winding connected to the electric generator K driven by the motive turbine Tm. The speed of the motor M can be pressor G and from there into the combustion controlled by means cf-a rheostat r. The speedof 2 I themotor M is thus adjustable and consequently the gas discharge supplied by the compressor G may be controlled.

' In Figure 5, the compression of the combustible gas is effected in two distinct stagesconnected in series. The low pressure portion of the compression is efiected in a fan V mounted on the shaft of the compressor C. The high-pressure portion is effected in a volumetric compressor G operated by a motor M (electric for example) the speed of. which can be controlled as mentioned above. a

Figure 6 relates to the third embodiment of the invention. A complementary liquid fuel isv utilized which is supplied by piping a, and on which the regulation is effected by means of a valve 11. In the example represented by this figure, the air compressor C and the gas compressor G are mounted on the same shaft (it could be otherwise) and the gas and the complementary fuel are burned in one and the same combustion chamber Ch.

In all these figures, the gas turbine installation chosen by way of example is of a particular type. Of course, the invention applies to all other types of gas turbines, Whatever arrangements and groupings are adopted, whether refrigerating means, regenerators, reheaters, etc. are utilized or not.

What I claim is:

In a thermal turbine motive unit, the combination of a motive turbine; an auxiliary turbine; a second auxiliary turbine; an air compressor driven by the first auxiliary turbine; a fuel compressor driven by the second auxiliary turbine; a combustion chamber, to which air and fuel are supplied by the compressors, respectively, the heated air from the combustion chamber being supplied to all three turbines; and means for controlling the flow of air to the second auxiliary turbine.

MARCEL HENRI LOUIS SEDILLE. 

